A New Simulation Method for 3D Propellant Grain Burn Analysis of Solid Rocket Motor  

固体火箭发动机三维药柱燃烧仿真的新方法

作　　者：方蜀州[1] 胡克娴[1] 张平[1] 

机构地区：[1]北京理工大学飞行器工程系

出　　处：《Journal of Beijing Institute of Technology》1995年第2期214+207-214,共9页北京理工大学学报（英文版）

摘　　要：Describes a new computer program (Regress-3D) to simulate the regression of complex 3D grain cavity and calculate the burning surface area. It has a large region of applicability in solid rocket motor design and has made new improvements compared with other available codes. User can easily and rapidly build his initial grain shapes and then obtain geometric information of his design. Considering with the calclulting results, redesigning can be performed as desire until reaching at the satisfied result. Advantages and disadvantages of this method are also discussed.研究和开发了一种新的固体火箭发动机复杂三维药柱内腔燃烧推移和燃面计算的仿真方法和程序，该程序大大扩展了固体火箭发动机的设计能力，较国内现有的同类程序有明显改进．用户利用它可简捷地构造出药柱的初始形状，并获得设计所需的几何参数，根据这些计算结果进行再设计，直至达到满意的结果为止．文中也讨论了这一方法的优势与不足．

关 键 词：solid propellant rocket engines propellant grains computerized simulation COMBUSTION 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]